Removable window system for space vehicles

ABSTRACT

A method for manipulating a window system in a platform is provided. A biasing system may be removed that biases a retention frame toward a support frame while the support frame and the retention frame hold a window pane. The retention frame may be removed after removing the biasing system. The window pane may be removed.

This application is a divisional of U.S. patent application Ser. No.13/279,620, filed on Oct. 24, 2011, now U.S. Pat. No. 9,221,533, thecontents of which are incorporated herein by reference in entirety.

GOVERNMENT LICENSE RIGHTS

This application was made in the performance of work under NationalAeronautics and Space Administration (NASA) Contract No. NNK11MS035 andis subject to the provisions of Section 305 of the National Aeronauticsand Space Act of 1958 (72 Stat. 435: 42 U.S.C. 2457.) The United StatesGovernment has certain rights in this application.

BACKGROUND INFORMATION

1. Field

The present disclosure relates generally to vehicles and, in particular,to space vehicles. Still more particularly, the present disclosurerelates to a removable window system for a spacecraft.

2. Background

Spacecraft may have platforms designed for operation in outer space. Aspacecraft may take various forms. For example, a spacecraft may be aspace station, a space shuttle, a capsule, a space plane, and otherplatforms that may enter outer space.

Some spacecraft may be designed to repeatedly be launched into space andre-enter the atmosphere. These types of spacecraft may be subjected totemperatures that may reach over about 1,500 degrees Celsius whenre-entering the atmosphere. Further, loads also may be placed ondifferent structures of the spacecraft during re-entry as well as duringlaunching of the vehicle into space.

These types of events may result in undesired inconsistencies in windowsin a spacecraft. For example, without limitation, a window may notprovide the optical clarity that may be desired for observing objectsoutside of the spacecraft. As a result, windows may be reworked orreplaced after re-entry and landing on the earth. In another example, awindow may not have a desired level of strength.

After a spacecraft has returned to Earth, spacecraft may be inspected todetermine whether inconsistencies may be found on windows and/or otherlocations on the spacecraft. If inconsistencies are found in a windowpane, the window pane may be replaced. Various components of the windowsystem may be removed to reach the window pane, remove the window pane,and/or replace the window pane. These different components may then bereassembled. Inspecting and reworking windows may be more time consumingand costly than desired.

Therefore, it would be advantageous to have a method and apparatus thattakes into account at least some of the issues discussed above as wellas possibly other issues.

SUMMARY

In one advantageous embodiment, a method for manipulating a windowsystem in a platform is provided. A biasing system may be removed thatbiases a retention frame toward a support frame while the support frameand the retention frame hold a window pane. The retention frame may beremoved after removing the biasing system. The window pane may beremoved.

In yet another advantageous embodiment, a method for manipulating awindow system in a platform is provided. A biasing system may be removedthat biases a retention frame toward a support frame while the supportframe and the retention frame hold a window pane. The retention framemay have an L-shape. The retention frame may be removed after removingthe biasing system. The window pane may be removed.

In yet another advantageous embodiment, a method for manipulating awindow system in a spacecraft is provided. A thermal protection systemmay be removed from the window system. A number of springs in a biasingsystem may be removed that biases a retention frame toward a supportframe while the support frame and the retention frame hold a windowpane. A first portion of the number of springs are configured to contactthe retention frame and a second portion of the number of springs isconfigured to engage a channel in the support frame. The support framemay be connected to a structure for the spacecraft by a fastener system.The retention frame may be removed after removing the biasing system.The retention frame may have an L-shape with a base and a flangeextending from the base. A sealing system in contact with the windowpane may be removed after removing the retention frame. The sealingsystem in contact with the window pane, the support frame, and theretention frame may form a seal for the window pane. The window pane maybe removed. A new window pane may be placed on the support frame. Thesealing system may be replaced. The retention frame may be replaced. Thebiasing system may be replaced such that the retention frame and thesupport frame hold the new window pane. The thermal protection systemmay be replaced.

The features, functions, and advantages may be achieved independently invarious embodiments of the present disclosure or may be combined in yetother embodiments in which further details can be seen with reference tothe following description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed characteristic of the advantageousembodiments are set forth in the appended claims. The advantageousembodiments, however, as well as a preferred mode of use, furtherobjectives, and advantages thereof will best be understood by referenceto the following detailed description of an advantageous embodiment ofthe present disclosure when read in conjunction with the accompanyingdrawings, wherein:

FIG. 1 is an illustration of a platform in which a window system may beimplemented in accordance with an advantageous embodiment;

FIG. 2 is an illustration of a spacecraft in accordance with anadvantageous embodiment;

FIG. 3 is an illustration of a window system in accordance with anadvantageous embodiment;

FIG. 4 is an illustration of an exploded view of a window system inaccordance with an advantageous embodiment;

FIG. 5 is an illustration of a cross-sectional view of a window systemin accordance with an advantageous embodiment;

FIG. 6 is an illustration of a portion of a window system in accordancewith an advantageous embodiment;

FIG. 7 is another illustration of a portion of a window system inaccordance with an advantageous embodiment;

FIG. 8 is another illustration of a portion of a window system inaccordance with an advantageous embodiment;

FIG. 9 is an illustration of a flowchart of a process for manipulatingcomponents in a window system in accordance with an advantageousembodiment;

FIG. 10 is an illustration of a platform manufacturing and servicemethod in accordance with an advantageous embodiment; and

FIG. 11 is an illustration of a platform in which an advantageousembodiment may be implemented.

DETAILED DESCRIPTION

The advantageous embodiments recognize and take into account one or moreconsiderations. For example, without limitation, the advantageousembodiments recognize and take into account that replacing a window panein a window system may take more time than desired. The number of partsthat are removed and replaced in replacing a window pane or removing awindow pane for rework may be numerous enough that the amount of timeincreases beyond what may be desired. Further, with the increased amountof time and labor needed, the cost for replacing window panes in awindow system also may be greater than desired.

The different advantageous embodiments recognize and take into accountthat in currently used window systems, numerous fasteners may be removedto allow access to a window pane. For example, without limitation, awindow system may have 60 or more fasteners that may be removed toremove a window pane. Further, these fasteners and/or new fasteners maybe installed when the window pane is replaced after rework or a newwindow pane is placed into the window system.

Therefore, the different advantageous embodiments recognize and takeinto account that avoiding removal of fasteners in a fastener system maybe desirable when removing a window pane from a window system, placing awindow pane in a window system, or a combination of the two.

Thus, the advantageous embodiments provide a method and apparatus for awindow system for use in a vehicle. In one advantageous embodiment, thewindow system may comprise a window pane, a support frame, a retentionframe, and a biasing system. The window pane may be configured tocontact a sealing system. The support frame may be configured to contactthe sealing system and support the window pane. The retention frame maybe configured to contact the sealing system and hold the window paneagainst the support frame. The biasing system may be configured to biasthe retention frame toward the support frame while the support frame andthe retention frame are in a configuration that holds the window pane.The window pane may be removed after removal of the retention frame.

With reference now to the figures and, in particular, with reference nowto FIG. 1, an illustration of a platform in which a window system may beimplemented is depicted in accordance with an advantageous embodiment.In this illustrative example, platform 100 may be spacecraft 102. Windowsystem 104 may be an example of a window system in spacecraft 102. Inthis illustrative example, window system 104 may comprise window pane106, sealing system 108, support frame 110, retention frame 112, biasingsystem 114, and thermal protection system 115.

In these illustrative examples, support frame 110 may be comprised ofmaterial selected from one of a metal, a metal alloy, aluminum,titanium, a fiber reinforced composite, a ceramic composite, and/or someother suitable material. Retention frame 112 may be comprised of amaterial similar to that of support frame 110. The material used forretention frame 112 may be the same or different from the material usedfor support frame 110. As depicted, support frame 110 may be associatedwith structure 116. Structure 116 may be external structure 118.

When one component is “associated” with another component, theassociation is a physical association in these depicted examples. Forexample, without limitation, a first component, support frame 110, maybe considered to be associated with a second component, structure 116,by being secured to the second component, bonded to the secondcomponent, mounted to the second component, welded to the secondcomponent, fastened to the second component, and/or connected to thesecond component in some other suitable manner. The first component alsomay be connected to the second component using a third component, suchas fastener system 120. The first component may also be considered to beassociated with the second component by being formed as part of and/oran extension of the second component.

In these illustrative examples, support frame 110 may be associated withexternal structure 118 through at least one of fastener system 120 andthermal protection system 115. Thermal protection system 115 mayindirectly connect support frame 110 to external structure 118.

As used herein, the phrase “at least one of”, when used with a list ofitems, means different combinations of one or more of the listed itemsmay be used and only one of each item in the list may be needed. Forexample, “at least one of item A, item B, and item C” may include, forexample, without limitation, item A or item A and item B. This examplealso may include item A, item B, and item C, or item B and item C.

In other examples, “at least one of” may be, for example, withoutlimitation, two of item A, one of item B, and ten of item C; four ofitem B and seven of item C; and other suitable combinations.

In these illustrative examples, fastener system 120 may comprisefasteners 122. Removal of fasteners 122, however, may be unnecessary inremoving window pane 106.

As depicted, window pane 106 may comprise a material selected from atleast one of silicone, polycarbonate, and/or other suitable materials.The material may be selected based on a desired use for window pane 106.

For example, without limitation, the materials used for window pane 106may be selected to have number of properties 124. Number of properties124 may include the desired level of at least one of an optical clarity,thermal insulation, toughness, and/or other suitable properties. As usedherein, a “number”, when used with reference to items, means one or moreitems. For example, “number of properties 124” is one or moreproperties.

In the illustrative examples, window pane 106 may be held in placewithin window system 104 by support frame 110 and retention frame 112.In these illustrative examples, support frame 110 may have supportflange 126. Support flange 126 may extend from support frame 110 and maybe configured to support window pane 106. Retention frame 112 may haveretention flange 128. Retention flange 128 may be configured to contactwindow pane 106. In these illustrative examples, the contact may be anindirect contact.

In particular, support frame 110 indirectly supports window pane 106through sealing system 108. More specifically, sealing system 108 may beconfigured to contact window pane 106 and support frame 110. Inparticular, sealing system 108 may contact support flange 126 on supportframe 110. Additionally, sealing system 108 also may be configured tocontact window pane 106 and retention frame 112. Further, sealing system108 may also contact support frame 110 and retention frame 112. Morespecifically, sealing system 108 may contact retention flange 128 onretention frame 112.

In these illustrative examples, window pane 106 may not directly contactsupport frame 110 and retention frame 112 when window pane 106 is heldin place by these components in window system 104. In other words,support frame 110 and retention frame 112 may indirectly contact windowpane 106 through sealing system 108.

As depicted, sealing system 108 may comprise number of seals 130. Numberof seals 130 may include at least one of number of pressure seals 132and number of thermal seals 134.

The material used for a seal in number of seals 130 may depend onwhether the seal is a seal within number of pressure seals 132 or numberof thermal seals 134. The material may be selected from one of anelastomeric material, rubber, silicone, or other suitable materials.

In these illustrative examples, biasing system 114 may be configured tobias retention frame 112 toward support frame 110. In particular,biasing system 114 may bias retention flange 128 toward support flange126 in the direction of arrow 135 with window pane 106 being locatedbetween the flanges.

In the illustrative examples, biasing system 114 may be number ofbiasing structures 136. A biasing structure in number of biasingstructures 136 may take different forms. For example, withoutlimitation, a biasing structure may be a spring, an elastic material, orsome other suitable component.

Number of biasing structures 136 may engage support frame 110. Inparticular, number of biasing structures 136 may be placed into numberof channels 138 in surface 140 of support frame 110. In theseillustrative examples, thermal protection system 115 may cover at leastone of retention frame 112 and external structure 118. Thermalprotection system 115 may protect other components in window system 104from heat that may result from operation of spacecraft 102.

When window pane 106 is located between support flange 126 and retentionflange 128 with number of biasing structures 136 engaged in number ofchannels 138, window system 104 may be in fixed configuration 144.

In particular, retention flange 128 may not be removable in a mannerthat allows for removal of window pane 106. As a result, window pane 106may be held in place within window system 104 by retention flange 128 onretention frame 112 and by support flange 126 on support frame 110.

When number of biasing structures 136 is removed from number of channels138, window system 104 may be in removable configuration 146. When inremovable configuration 146, retention frame 112 may be moved in amanner that allows window pane 106 to be removed from window system 104.In particular, retention flange 128 may be moved away from supportflange 126 such that window pane 106 may be removed from window system104.

Window pane 106 may then be reworked or replaced by new window pane 148.These operations with respect to window pane 106 may be performedwithout the time and effort involved in removing fasteners. In theseillustrative examples, removal of fasteners 122 may not be needed toremove window pane 106 from window system 104.

In this manner, removing window pane 106 for any reason may be performedmore quickly as compared to currently available window systems. Removalof large numbers of fasteners may be unnecessary to remove window pane106. Further, if window pane 106 is replaced with new window pane 148,installation of new window pane 148 may be performed without installingfasteners in fastener system 120.

For example, without limitation, fasteners 122 in fastener system 120may be about 60 fasteners. If removal of the 60 fasteners is needed toremove window pane 106, the amount of time may be greater than removingnumber of biasing structures 136 from number of channels 138. In oneillustrative example, two biasing structures may be present in number ofbiasing structures 136 that fit into one channel in number of channels138. The time needed to remove these two biasing structures in number ofbiasing structures 136 from one channel in number of channels 138 may beless than the time required to remove all 60 fasteners.

The illustration of window system 104 in platform 100 in FIG. 1 is notmeant to imply physical or architectural limitations to the manner inwhich an advantageous embodiment may be implemented. Other components inaddition to or in place of the ones illustrated may be used. Somecomponents may be unnecessary. Also, the blocks are presented toillustrate some functional components. One or more of these blocks maybe combined, divided, or combined and divided into different blocks whenimplemented in an advantageous embodiment.

For example, in other illustrative examples, platform 100 may have anumber of additional window systems in addition to window system 104.Further, platform 100 may take other forms other than spacecraft 102.Platform 100 may be, for example, without limitation, a mobile platform,a stationary platform, a land-based structure, an aquatic-basedstructure, a space-based structure, or some other suitable type ofplatform. More specifically, an advantageous embodiment may be appliedto, for example, without limitation, a vehicle, an aircraft, a spacecapsule, a space shuttle, a submarine, or some other suitable platform.

As yet another illustrative example, although support frame 110 isdepicted as being connected to structure 116 in the form of externalstructure 118, support frame 110 may be connected to other structures.For example, structure 116 may be an internal structure. Support frame110 may be connected to an internal structure because removal offastener system 120 and support frame 110 may not be needed to replacewindow pane 106. In yet another illustrative example, another type ofsystem other than thermal protection system 115 may be used. Forexample, without limitation, a metal cover, or some other suitablestructure may be used in place of and/or in addition to thermalprotection system 115.

With reference now to FIG. 2, an illustration of a spacecraft isdepicted in accordance with an advantageous embodiment. In thisillustrative example, spacecraft 200 is an example of an implementationfor spacecraft 102 in FIG. 1. Spacecraft 200 is shown in a perspectiveview. In this example, spacecraft 200 may be capsule 202. Spacecraft 200may have window system 204 and window system 206. In this illustrativeexample, window pane 208 may have trapezoidal shape 210, while windowpane 212 may have circular shape 214. Of course, window pane 208 mayhave other shapes. For example, without limitation, window pane 212 maybe an oval, a square, a hexagon, or some other suitable shape. Amore-detailed view of window system 204 in section 216 may be seen inFIG. 3.

With reference now to FIG. 3, an illustration of a window system isdepicted in accordance with an advantageous embodiment. In thisillustrative example, a more-detailed view of window system 204 insection 216 from FIG. 2 is depicted. In this illustrative example,thermal protection system 300 in window system 204 covers differentcomponents of window system 204 other than window pane 208. Thermalprotection system 300 may be removed to perform maintenance operationson window pane 208.

With reference now to FIG. 4, an exploded view of a window system isdepicted in accordance with an advantageous embodiment. In thisillustrative example, an exploded view of window system 204 is depicted.In this exploded view, window system 204 may comprise thermal protectionsystem 300, biasing system 400, retention frame 402, window pane 208,and support frame 404. Further, window system 204 may also include afastener system and a sealing system, which are not shown in this view.In this illustrative example, these components may be connected to anexternal structure (not shown).

With reference now to FIG. 5, an illustration of a cross-sectional viewof a window system is depicted in accordance with an advantageousembodiment. As depicted, a cross-sectional view of window system 204taken along lines 5-5 in FIG. 3 is shown.

As depicted, retention frame 402 has L-shape 500. In particular,retention frame 402 has base 502 with flange 504 extended substantiallyperpendicular from base 502. In this illustrative example, support frame404 has base 506 and flange 508. Flange 504 and flange 508 may besubstantially parallel to each other in this depicted example. Asillustrated, window pane 208 may be located between flange 504 ofretention frame 402 and flange 508 of support frame 404.

In this illustrative example, surface 512 of window pane 208 contactsseal 514 in sealing system 515. As depicted, seal 514 may be a thermalseal. Surface 516 of window pane 208 contacts seal 518 in sealing system515. In these illustrative examples, seal 518 may be a pressure seal. Inparticular, seal 518 may be a redundant pressure seal. Surface 520 ofwindow pane 208 may contact seal 522 in sealing system 515. Seal 522 maybe a pressure seal in these illustrative examples.

In turn, seal 514 and seal 522 may contact surface 540 of retentionframe 402. In a similar fashion, seal 518 may contact surface 525 ofsupport frame 404.

In this illustrative example, seal 524 and seal 526 in sealing system515 may be located between retention frame 402 and support frame 404.Seal 524 may be a thermal seal, and seal 526 may be a pressure seal.

In these illustrative examples, seal 528 and seal 530 may be locatedbetween support frame 404 and external structure 410. Seal 530 may be apressure seal, and seal 528 may be a redundant pressure seal for seal530. In this illustrative example, support frame 404 may be connected toexternal structure 410 through fasteners, such as fastener 532, infastener system 533.

As illustrated, number of springs 534 in biasing system 400 may beengaged with support frame 404. In these illustrative examples, numberof springs 534 may be two springs. In other illustrative examples,number of springs 534 may be some other number of springs. In stillother advantageous embodiments, biasing system 400 may only include asingle spring, depending on the particular implementation.

As depicted, a portion of number of springs 534 may be located inchannel 536 in surface 540 of support frame 404. In this illustrativeexample, number of springs 534 also contacts surface 542 of retentionframe 402. In particular, number of springs 534 may contact surface 542on flange 504 of retention frame 402. Number of springs 534 may becomprised of titanium, steel, a steel alloy, and other suitablematerials.

In this illustrative example, number of springs 534 applies a force indirection 544. This force may cause flange 504 to move toward flange 508in direction 544 with window pane 208 in between these flanges. Thisconfiguration may hold window pane 208 in place within window system204.

In FIGS. 6-8, an illustration of components removed to access windowpane 208 is depicted in accordance with an advantageous embodiment.Turning first to FIG. 6, an illustration of a portion of a window systemis depicted in accordance with an advantageous embodiment. In thisillustrative example, thermal protection system 300 is shown as removedfrom around window system 204. When thermal protection system 300 isremoved, number of springs 534 may be accessed as part of a process togain access to window pane 208. Thermal protection system 300 may beattached to spacecraft 200 in a number of different ways. For example,thermal protection system 300 may be attached using fasteners, adhesive,and/or other suitable attachment mechanisms.

Turning next to FIG. 7, an illustration of a portion of a window systemis depicted in accordance with an advantageous embodiment. In thisexample, number of springs 534 has been removed from channel 536. Withnumber of springs 534 removed from channel 536, retention frame 402 mayno longer be biased in direction 544.

As a result, retention frame 402 may be moved in the direction of arrow700. Moving retention frame 402 in the direction of arrow 700 maydisengage retention frame 402 from holding window pane 208 in place inwindow system 204.

In FIG. 8, an illustration of a portion of a window system is depictedin accordance with an advantageous embodiment. As depicted, retentionframe 402 has been removed along with seals 514, 522, 524, and 526. Withthese components removed, window pane 208 may be removed. This removalof window pane 208 may be performed without removing fasteners, such asfastener 532. In this manner, easier removal of window pane 208 may beperformed by removing number of springs 534 (not shown) rather thanfasteners in fastener system 533.

The different components shown in FIGS. 2-8 may be combined withcomponents in FIG. 1, used with components in FIG. 1, or a combinationof the two. Additionally, some of the components illustrated in FIGS.2-8 may be illustrative examples of how components shown in block formin FIG. 1 can be implemented as physical structures.

With reference now to FIG. 9, an illustration of a flowchart of aprocess for manipulating components in a window system is depicted inaccordance with an advantageous embodiment. This process may beimplemented with window system 104 in FIG. 1.

The process may begin by removing thermal protection system 115 fromwindow system 104 (operation 900). Biasing system 114 may then beremoved from window system 104 (operation 902). Thereafter, retentionframe 112 may be removed from window system 104 (operation 904). Anumber of seals in number of seals 130 may be removed after removingretention frame 112 (operation 906). The number of seals may be pressureseals, thermal seals, or some combination thereof. Thereafter, windowpane 106 may be removed from window system 104 (operation 908), with theprocess terminating thereafter.

The different operations illustrated in FIG. 1 may be performed inreverse order to secure a window pane in window system 104. In theseillustrative examples, these operations may be performed to install newwindow pane 148.

Thus, the different advantageous embodiments provide a method andapparatus for a window system on a platform. In these illustrativeexamples, the platform may be a spacecraft with a window system, such aswindow system 104. Assembly and disassembly may be performed more easilyand more quickly as compared to currently used window systems. Windowpane 106 may be accessed by removing biasing system 114 and retentionframe 112. This removal of components may be performed without removingfasteners 122 in fastener system 120. In this manner, the time, cost, orboth for replacing window panes on a space vehicle may be reduced.

Advantageous embodiments of the disclosure may be described in thecontext of platform manufacturing and service method 1000 as shown inFIG. 10 and platform 1100 as shown in FIG. 11. Turning first to FIG. 10,an illustration of a platform manufacturing and service method isdepicted in accordance with an advantageous embodiment. Duringpre-production, platform manufacturing and service method 1000 mayinclude specification and design 1002 of platform 1100 in FIG. 11 andmaterial procurement 1004.

During production, component and subassembly manufacturing 1006 andsystem integration 1008 of platform 1100 in FIG. 11 may take place.Thereafter, platform 1100 in FIG. 11 may go through certification anddelivery 1010 in order to be placed in service 1012. While in service1012 by a customer, platform 1100 in FIG. 11 may be scheduled forroutine maintenance and service 1014, which may include modification,reconfiguration, refurbishment, and other maintenance or service.

Each of the processes of platform manufacturing and service method 1000may be performed or carried out by a system integrator, a third party,and/or an operator. In these examples, the operator may be a customer.For the purposes of this description, a system integrator may include,without limitation, any number of spacecraft manufacturers andmajor-system subcontractors; a third party may include, withoutlimitation, any number of vendors, subcontractors, and suppliers; and anoperator may be an airline, a leasing company, a military entity, aservice organization, and so on.

With reference now to FIG. 11, an illustration of a platform is depictedin which an advantageous embodiment may be implemented. In thisillustrative example, platform 1100 may be produced by platformmanufacturing and service method 1000 in FIG. 10. Platform 1100 mayinclude frame 1102 with a plurality of systems 1104 and interior 1106.Examples of plurality of systems 1104 may include one or more ofpropulsion system 1108, electrical system 1110, hydraulic system 1112,environmental system 1114, and thermal protection system 1116.

Although an aerospace example is shown, different advantageousembodiments may be applied to various industries, such as the spacecraftindustry, the aircraft industry, the automotive industry, the shipindustry, and/or other suitable industries. Platform 1100 may also takevarious forms. For example, without limitation, platform 1100 may beselected from one of a mobile platform, a stationary platform, aland-based structure, an aquatic-based structure, a space-basedstructure, a vehicle, an aircraft, a space capsule, a space shuttle, asubmarine, and other suitable types of platforms.

Apparatuses and methods embodied herein may be employed during at leastone of the stages of spacecraft manufacturing and service method 1000 inFIG. 10. In one illustrative example, components or subassembliesproduced in component and subassembly manufacturing 1006 in FIG. 10 maybe fabricated or manufactured in a manner similar to components orsubassemblies produced while platform 1100 is in service 1012 in FIG.10.

As yet another example, a number of apparatus embodiments, methodembodiments, or a combination thereof may be utilized during productionstages, such as component and subassembly manufacturing 1006 and systemintegration 1008 in FIG. 10. A number, when referring to items, meansone or more items. For example, a number of apparatus embodiments is oneor more apparatus embodiments. A number of apparatus embodiments, methodembodiments, or a combination thereof may be utilized while spacecraft1100 is in service 1012 and/or during maintenance and service 1014 inFIG. 10. The use of a number of the different advantageous embodimentsmay substantially expedite the assembly of and/or reduce the cost ofplatform 1100.

In particular, at least one of a method and apparatus for anadvantageous embodiment may be implemented for a window system inplatform 1100. With a window system, such as window system 104, removaland installation of window panes may be performed more quickly, for lesscost, or some combination thereof.

The description of the different advantageous embodiments has beenpresented for purposes of illustration and description and is notintended to be exhaustive or limited to the embodiments in the formdisclosed. Many modifications and variations will be apparent to thoseof ordinary skill in the art. Further, different advantageousembodiments may provide different advantages as compared to otheradvantageous embodiments. The embodiment or embodiments selected arechosen and described in order to best explain the principles of theembodiments, the practical application, and to enable others of ordinaryskill in the art to understand the disclosure for various embodimentswith various modifications as are suited to the particular usecontemplated.

What is claimed is:
 1. A method for manipulating a window system in aplatform, the method comprising: removing a first spring and a secondspring in a biasing system that biases a retention frame toward asupport frame while the support frame and the retention frame hold awindow pane, wherein a first portion of the first spring is configuredto contact the retention frame and a second portion of the first springis configured to engage a channel in the support frame, and wherein afirst portion of the second spring is configured to contact theretention frame and a second portion of the second spring is configuredto engage the channel in the support frame; removing the retention frameafter removing the biasing system; and removing the window pane.
 2. Themethod of claim 1 further comprising: removing a sealing system incontact with the window pane after removing the retention frame.
 3. Themethod of claim 2, wherein the sealing system in contact with the windowpane, the support frame, and the retention frame forms a seal for thewindow pane.
 4. The method of claim 2, wherein the retention framecomprises: a base; and a flange extending from the base, wherein theflange contacts the sealing system.
 5. The method of claim 1 furthercomprising: removing a thermal protection system prior to removing thebiasing system.
 6. The method of claim 1 further comprising: placing anew window pane on the support frame; replacing the retention frame; andreplacing the biasing system such that the retention frame and thesupport frame hold the new window pane.
 7. The method of claim 1,wherein the support frame is connected to a structure for the platformby a fastener system.
 8. The method of claim 1, wherein the retentionframe has an L-shape.
 9. The method of claim 1, wherein the platform isselected from one of a mobile platform, a stationary platform, aland-based structure, an aquatic-based structure, a space-basedstructure, a vehicle, an aircraft, a space capsule, a space shuttle, anda submarine.
 10. The method of claim 1, wherein a first portion of thebiasing system is configured to contact the retention frame and a secondportion of the biasing system is configured to engage the channel in thesupport frame.
 11. The method of claim 10, wherein the biasing system isa single continuous member.
 12. A method for manipulating a windowsystem in a platform, the method comprising: removing a first spring anda second spring in a biasing system that biases a retention frame towarda support frame while the support frame and the retention frame hold awindow pane, wherein a first portion of the first spring is configuredto contact the retention frame and a second portion of the first springis configured to engage a channel in the support frame, and wherein afirst portion of the second spring is configured to contact theretention frame and a second portion of the second spring is configuredto engage the channel in the support frame; removing the retention frameafter removing the biasing system; and removing the window pane; whereinthe retention frame has an L-shape.
 13. The method of claim 12, whereina first portion of the biasing system is configured to contact theretention frame and a second portion of the biasing system is configuredto engage the channel in the support frame.
 14. The method of claim 13,wherein the biasing system is a single continuous member.
 15. The methodof claim 12, further comprising: removing a sealing system in contactwith the window pane after removing the retention frame.
 16. The methodof claim 12, further comprising: removing a thermal protection systemprior to removing the biasing system.
 17. The method of claim 12,further comprising: placing a new window pane on the support frame;replacing the retention frame; and replacing the biasing system suchthat the retention frame and the support frame hold the new window pane.18. The method of claim 12, wherein the sealing system is in contactwith the window pane, the support frame, and the retention frame forms aseal for the window pane.
 19. The method of claim 12, wherein theretention frame comprises: a base; and a flange extending from the base,wherein the flange contacts the sealing system.
 20. A method formanipulating a window system in a spacecraft, the method comprising:removing a thermal protection system from the window system; removing anumber of springs in a biasing system that biases a retention frametoward a support frame while the support frame and the retention framehold a window pane in which the support frame is connected to astructure for the spacecraft by a fastener system, wherein a firstportion of the number of springs are configured to contact the retentionframe and a second portion of the number of springs is configured toengage a channel in the support frame; removing the retention frameafter removing the biasing system in which the retention frame has anL-shape with a base and a flange extending from the base; removing asealing system in contact with the window pane after removing theretention frame in which a sealing system in contact with the windowpane, the support frame, and the retention frame form a seal for thewindow pane; removing the window pane; placing a new window pane on thesupport frame; replacing the sealing system; replacing the retentionframe; replacing the biasing system such that the retention frame andthe support frame hold the new window pane; and replacing the thermalprotection system.